Rigid aircraft



June 14, 1927.- 1,632,641

F. BAUER RIGID AIRCRAFT Filed Jan. 2, 1926 5 Sheets-Sheet 1 avweutoz 1927 I 1 632,641 June 14, F. BAUER RIGID AIRCRAFT Filed Jan. a; 1926 5 Sheets-Sheet 2 I avwwntoz June '14, 1927. 1,632,641

- F. BAUER RIGID AIRCRAFT Fild Jan. 2, 1926 5 Sheets-Sheet 4 Patented June 14, 1927.

FRANK BAUER, 01" w iL I AMsviLLnI YORK:

RIGID aincnan'rl iA pp'liceti on 'filed JanuaIy Z, Serial New 78, 852

inventieirrelates to improvements in rigid ail-crafts and my Objects beingi ,First, that th'isrigigil aircraft is a coinbination airship an I a airplane. I i

fiecendfihat lillSCQlllFlQtQlY built of metal ftt hat is, the hull, planes, and ears, but not the gas-cells, etc, a a W 4 I )Thii d that the special contour and shape 01" this rigid aircraft, thehnll (body) is nine times longer than its height, twice as wide as its height its Width and height tapering; and curving ,at" the after end, the

tapering beginning about one third of aircraits length from the stern end, it has a round I flat-tish how; this cent-our being intensified by the addition of t ventyspecially' shaped planes (Wings) tae tened to the hull at specifiedflocations. I

Fourth, that there is a special meta lbackhone construction through this rigid aircraft tron'i bew toistern composed of Win tical and diagonal girders fastened to upper a mhloweihorizontal 'boxbearns. 4 a Fifth, that fromthis baehbcne; (that is from the boxbeanipart.) smaller rib I girders rim vertically and horizontally te term the :Frame-Wdrk and contour o tthis rigid aircraft, also that bet ween these" srnaller rib girdersthei'e are Wires, attachedtd the ribs and te one another helping form the framework M gixth, that there is a thin sheet metal ontside covering fastened Ion to this a-ircrafts fIml'lQ-WOl'k.

Seventh that this aircrafts frame-Work is as be kept tightened and tantin a special manner by the 'useof metal cables, placed at meme inside tlieihnll", and tightened and;

' stened to the tram eworkj ith turnbn clrles.

' Eighth; that the boxb eams and girders, areio t a special design and construction and that they are of innetal.

Ninth, that twent fastened in their proper Tenth that these planes (Wings) are of a special design and c0nstrncti0i1;and are eatirely'bnilt of netal. i

Eleventh, that there is a special methedj (w ngsyare fastened to in which the planes the hull ef this rigid aircraft.

Twelfth, that there is a special systenief maneuvering and balancing (trimming) this maneuvering and rigid aircraft.

La ng as location to: the hull.

- lhirte'en'th, that th'ereis especial. arrange? in'nt 0t 'mecfha'nisi" s "t j attain this syste'inlof V balancing this 'rigida'ir5 craft. I 9 a Eonrte'enth', that the'reis a specialfarrange; men; for the twenty-tomgas-celIsthrOiigh out th e hiill of this rigid air'cra ttl llifteenth, tl'iatthere is a special 'ar angeinei t which is that o 'ftastening the main car onftight and flush against "thetbpef "the '1 attain these ebjectsjby the m chanisms,- 7

constructions and arrangements illustrated in the accompany ng drawings; in w'hlch Fig; lls a lanch-aw'mg of the entire Fig. 16 shotvsan elevation section orfplane and jrib girder. s a h lIslbWs thefspciial systein oif arranging the mechanisms that are? used 61 a 1g. Qj'is afsitile' elei ation Viewed 'theeii-l are rigidiaiircraftj v W ,3 is an elevationslibwin across sectionfth'rengh' the center 'of meg watt, a

v Fig. 4 is ap1an'-'sectiOnofthehiill and 'p1anes. I I Q fl 'Figi 5 is anelilation'fsectien of the hull a1'1d pla'nes. r -Fig. and Fig; 8 are plan vietvsOfthe l bi ld a 7 i i v a Fig. 7 s a cross seamen elevation 0% a rib girder; a, Fig, 9 is a side elevation f jaq rib"? girder; Fig; 10 is a plan V l eilV of'a boxb'e'arh. Fig. 11, 1116per part shows a cross sectiei' of a boxbeain and ldiver part'shetvsh "side elevation View of a vertical and diagonal girder f f a a '1' Fig. 12 shewsa section of the aircraft, in -p p :v a, a 'i 2 "Fig; 13 shew'sia plan section view'bf a p ie'q n -s a ca Fig. 14 shoc wsja side elevationet a =p1anes (w nei a a a Figqlisho'ws aperspeetiVe drawing of an e it ire; ip1a-1 e (Or wing)j maneuvering and balancing (trimming) this rigid aircraft.

Similar letters and numerals refer to similar parts throughout the various drawings.

The contour and shape of this rigid aircraft through the construction of the framework of the hull with the addition of the planes (wings) is acquired as follows:

Regarding the hull in making up the contour and shape of this rigid aircraft:

A the vertical and diagonal girders running the height of the aircraft are fastened by welding and riveting to B the boxbeams and these A girders and B boxbeams form the metal backbone of. this aircraft. This backbone runs the entire length of the aircraft and its outlines which show the contour and shape of this aircraft in elevation, run from the bow which is curved in a half circle and is shown in X in Fig. 2, elevation, continues slanting upward as f it meets X which designates the horizontal line of the aircrafts top, then it slants downward gradually as X until it develops into the point of the stern S, here it turns and runs slanting as X to X the bottom horizontal line, then it slants upward again as X to meet the curved bow This elevation outline of this aircraft just described is formed by the boxbeams B.

Running from the boxbeams B, to which they are fastened by welding and riveting and going around the aircraft vertically and horizontally and intersecting and fastened to one another are the metal rib-girders G which help form the framework as shown by Fig. 1 plan and Fig. 2, elevation, and these rib-girders help form the plan contour and shape of this aircraft by the outlines being formed by them as shown by the lines X X, X. and stern point S on Fig. l. The contour and shape of the aircraft by these rib-girders C shown in cross section through the center of the aircraft is shown in Fig. 3 by the lilies X These ribgirders C are fastened to the boxbeams B and to one another by welding and riveting and they are so spaced in this aircrafts fran'iework so as to give the maximum utility and serviceableness. Also the A vertical and diagonal girders which are fastenet'l to the upper and lower boxbeams B are so spaced in the backbone of this aircraft so as to give the maximum utility and service ableness. D are the wires fastened to the rib-girders C and to the boxbeams B and to one another at right angles and these wires D help form the framework. The outside thin sheet metal covering H is fastened to the framework by riveting and welding, shown in Fig. 1, Fig. 2 and Fig. Throughout the inside of" this aircrafts framework and spaced at the proper intervals are the metal cables E shown in Fig. 3 and Fig. 5, these cables are fastened to the framework with turnbucklcs and these cables E are used to tighten and brace and to keep taut the metal framework. Fig. at, plan, Fig. 5 elevation section and Fig. 12 perspective section, show the letters and numerals designating the various constructions of the framework in greater detail.

The contour and shape of this aircrafts hull is acquired by the above construction methods and formations and this contour and shape of the hull as follows:-It is nine times longer than its height, twice as wide as its height, its width and height tapering and curving to a point at the stern end, the tapering beginning about one third of the aircrafts length from the stern end; it has a round flattish bow. The contour and shape of this aircraft is exactly as illustrated in Fig. 1, Fig. 2 and Fig. 3 which show the curved, horizontal, vertical, slanting and all other lines in plan, elevation and cross-section views, that give the hull its contour and shape. Again. the designations X X, X, X*, S (and some other numerals and letters not yet mentioned such as those for the ars, tins, rudders, etc.) on the accompanying drawings, show the locations of these various line shapes and outlincs that make up the contour of the hull.

"tegarding the planes (wings) that: help make up the contour and shape of this rigid aircraft There are twenty specially designed metal planes Q which add to the contour and shape of this aircraft and these planes Q are fastened to the hull and they are placcd at the locations marked Z and Z on the drawings showing the hull and planes. The contourand shape of these metal planes (.1 are illustrated in Fig. I, Fig. ll and Fig. 15; the plan outline of such a plane Q is shown in Fig. l, (and Fig. 15,) starting at a point Q, it is shown as a straight line that runs to Q then diagonally in to Q thence in a straight line to Q", thence running at right angles, to Q. The concave and convex curves of these planes located in the width and height of each plane are shown in Fig. 14 by Q", Q Q. Q". (2 and Q. and run the full length of the plane. These metal planes are put on the hull in tri-plane etl'cct and are arranged so that the longest plane Q is on top; the next; plane below (Q? which is shorter than the first: the lowest plane is (3 which is the shortest. of the three. There are six sets of thei'e mental planes located on the hull. viz: three sets on each side; each plane is located at the place marked Z on the hull as shown in the drawings. Also between the last set of tri-planes and the point of the stern, on each side of the aircraft is a single metal plane th same size and shape as the planes Q These last two planes are located on the hull at Z. All the metal lilt) The chriwings end" descriptions showing theiiuinber, shape and locations of these p1dnes,'*added to the shepebtf thehull, cornpl'ete the oiitiines of the; contour ahd simple oitheehtire rig-id aircraft." Added to this or coerse are the out hhes that compose the passenger, power and Controlcars desiggirders v i I Regarding the speeml constr'iictioir of t-eth shown-'51s C Fig. 9 designated by C sh ows The 'special' design and eonstruet'ion in nietrl 'otstheho'xbeahis' B, and the vertical and dihgonaigirders'A and the rib girders C ure" acquired 'inthis in'aiine'r Regarding the specie design: I i The special triangular. design is "die shown in Fig. l' l and Hand is desig nated as A for the vertiealiandthese, inetai rib; girders; vertieal and diagoiiel girders 2H1: 'boztbeams, these are constructe'das' *follews 1- F01- the-'- xnetal ifibs which are tonnes of thee-pieces "riveted together; the'niain piece of thec rib' girder has eaeh'end bent,

asshoWniI'rFigQT designatedas C and on ni'ai h pi'e-ceare riveted the bent pieees hbiv these niet'al piee'esferefriveted, The edges of the ber'rt'pieoes of 'therrb girder are perfdi'eted with small holes which areehow'n in the plan views, Fig. GRBd'FigL-S andare These holes are usedfor designated as C fastening the W ires D on thehut'side of -the pieces andoii theinside-of the pieees for attaching the Wires or toggle li nes'Gc (see Fig; 5, Fig." 11'; Fig. 12am Fig; F16) Whi'ch framework; The same pi'joced'nre of con stru'ction is followed when Constructing the vertichi a'nddifagoiialgirders A lower part ll'e nd pai ts nittrkedA A2 and A For the'nieta'Y boxbeams B which are toiined oi four pi c'es riv'etedf together the two vertical pieces," which ar'e'the' two side pieces marked B are bent in at the ends, designzitedB' andorito these bent an-5.13 are riveted the two horizontal.

piete's marked]? which form theto'p and bottom parts of the bo xbea'ins. Thesenp per and" lower pieces Bfire perforated with diagonal These, speei'al constructions of the beams B,- vertieal n'id' diagonal girders A and the rib girders G are Welded end riveted together their proper locations to form the metal frarr'iework' 01 this rigid mew-rt. The construction and special design re gal the contour of the: twenty piiines ner:-

Tlle

specification: i Regarding the construction of one of these" pi *i'es" Qgga die sta'r'n ped rib is plaeed"at each end of thef 'plin'ie (wing) and at itl'i'efneeessiry intervening s-paeeshe'tiveen; 011 to these ribs 'tastened'the 1oiigthin metal squ'are edg'edpieties "Q exaetiy as triangular design Q t l'ie stz uli'rped o1 iiitv ehin'ed out O'Pth'ein the'vertieal and d i zigone! gii ders hoxbemns :ihd'iib girders have. l lzieh 'piz he 'rih Q has its'e tire line notched shoWn'in Fig; 1 1- -so that the-longthilrmetal squire edge'd p'ie'e'es Q fitii tothese notehesi cbntour 'und sha peef these piunes Q; has already bee'i'i'deseribed elsewhere ih this over the framework *coiisisting 'ofth'e 'inet The 'speciuhin'iihner in 'iwihich thetwenty (20) phinesare fzistenedto the hull is eX-aet- V 13 its shoii h oh the diawing'in ig. 1'8", designated Q This sho ii sxtl'ie 'slzii'ie (Wing) protiudi irg ins'i ieth'e hiiH Prihs so that the upper and loweifliiietal braces can be fastene'd' to the plef-i'ie Q'ai'id onto the hull ribs C. Additional "rib 5 girders C are p lzieed en this direr zifts framework w-hiateverireeiessaifyso that-there 71H be isirhsthntial" sink faces" on wviiicli to 'f'zistenf the planes we) Q;

In this ri' ir'it de of ajru'bberizedfabric Inuteriiiiaiid a'lent. manner thdt it will fit snugly in itsfspeci fijedjplace inside the framework Whbiieiipended with gas. These'eells arefarranged 7 aircraft there {a re "twenty fotir I v (24) gasfee'll envelo es (hallonets-or bags) in pairs, twelve pairs on eheh side of the bec'iz bone gifders throughout the entire lengthlo'f this aircraft. See sections of them designtitedG, onFig 1; Fig. 2,

Fig-I1; 112 and Fig. 17; The 'size' and shtipe oiFfthese' gas cells (hailonets or bags) is governed" bye e outline shape of height-:- Iii letigththeiel ls drehll ieq iai.

These gas-"cell's ere-fastened to the inside of. no

the framework with toggle-ropes or wires, GC The end of the toggle-rope or wire that is fastened to the gas-cell is divided into several strands and cemented to the gas-bag in crossfoot effect. The other end of the toggle-rope or wire, GC is fastened to the aircrafts framework through the small holes that perforate the girders and boxbeams.

The method to accomplish the manipulation of filling and emptying of the gas-cells, G, and the compresscd-gas-storage tanks, 0, so as to maneuver and balance (trimming) this rigid aircraft is as follows,

First, for filling gas-cells G:(see Fig. 17).

Close globe valves J between rotary (centrifugal) gas compressor P and compressedgasstorage tanks 0; open diaphragm valves I, pressure dial L is to be considered for regulation of pressure; open needle valve N between storage tanks 0 and manifold pipe M; open globe valves J between manifold pipe M and flexible connecting gas-cell pipes F the gas then flows at a pressure that may be regulated from the compressed-gasstorage tanks 0 through the gas-pipe (lines) K and all the other mentioned valves and pipes into the gas-cells G. The gas pipes and valves between the manifold pipe and the gas-cells may be opened and closed so that only certain gas-cells, either right side or left of this aircraft, either above or below, either front, middle or back gas-cells may be filled as desired.

Second, for emptying gas-cells G:(see Fig. 17).

Close needle valve N; close diaphragm valves 1; open globe valve J between rotary (centrifugal) gas compressor P and gasstorage-tanks t). The globe valves J (of the cells that are to be emptied) between the manifold pipe M and the flexible pipes F must. be open. Start and regulate the rotary compressor 1 and the rotary blower PP which blows the gas into the rotary compressor from the gas-cells. This rotary blower PP may be Qllll'llllillLt-Kl from this systeni. The rotary compressor P will receive the gas from the rotary blower, compress it, and then pump it through the gas pipes K and globe valves J, into the compressedgas-storage tanks t). The rotary blower and rotary con'ipressor may be regulated to move and compress as large a volume of gas as desired. The power to rotate the gas-blower PP and gas-compressor P is supplied by an auxiliary engine or motor I. P shows the belt drive from the auxiliary engine or I110- tor to the rotary blower and rotary compressor. One or many gas-cells may be emptied as desired just by adjusting the valves.

The various mechanisms, constructions and arrangements that comprise this system of maneuvering and balancing (trimming) this rigid aircraft by a controlled method of emptying the gas-cells (bags or ballonets) and compressed-gas-storage-tanks with the use of rotary compressor and blower, may be located in the most appropriate places (positions) in the control and power cars and inside this aircrafts hall on the passageways alongside the bottom of this aircrafts metal backbone so that this system may be used as eliiciently as possible.

The main car which is to be used for carrying passengers, freight and other articles is firmly fastened flush to the boxbeams and rib girders and metal hull covering by riveting onto the top of this aircrafts hull and is designated in the drawings as l in Fig. 1, Fig. 2, and Fig. 3. ,It is to be constructed of metal.

The control and power cars are to be used for housing the ofiicers and crew, the controlled system of maneuvering and balancing (trimming) the aircraft, the propelling engines and motors, wireless, the charts and all aeronautical instruments; these cars are designated in the drawings as 1 in Fig. 2 and Fig. 3. These cars are also to be built of metal and are riveted to the boxbeams, and girders, etc., by riveting flush onto the bottom of this aircrafts hull. All cars tit flush to this aircra't'ts hull.

The passageway which is designated as 25 in Fig. 2 is a vertical one and leads from main car 1 to the horizontal passageways 3" on the bottom of this aircrafts hull. This passageway 23 is a cylindrical metal one and persons may go from car 1 to the bottom passageways 3*, or vice versa, by means of an elevator or stairway or ladder.

The passageways on the bottom of the hull are horizontal ones and are designated as 3- in Fig. 2 and Fig. 23. These passageways 3" run the full length of the bottonrot' the hull on either side of the aircra'l'ts metal backbone. From this long passageway smaller passageways lead to the control and power cars 1-.

Along the main passageways 23-" are also placed fuel and water tanks also some trimming ballast tanks.

The stabilizing fins and rudders used to stealy and guide (steer) this aircraft are designated as 2 in Fig. l and Fig.

Items such as safety valves, a properly constructed bow or nose so that this aircra it can be fastened to a mooring mast, and all other necessary appliances that go with rigid aircra'l'ts of modern type, but are not claimed in my invention, are or may be used on this rigid aircraft.

1 am aware that prior to my invention. rigid airships have been made and flown. especially those originated by the (iermans. But these German designed types have proved their fragility and unsuccesstulness by their many disasters. However, due

credit must be given these Germantypes for they are the pioneers in the modern era of rigid airship building and flyin My invention will eliminate this fragility heretofore shown in rigidaircrafts as I have combined the principal features of both the rigid airship type and airplane type by using new original ideas in designing a safe and absolute airworthy rigid aircraft. 'My modern system of a controlled method of maneuvering and balancing (trimming), this rigid aircraft in emptying and filling the gas-cells (bags or ballonets) blower is an innovation in safetiness when guiding and maneuvering (assisted by the propelling engines or motors) an aircraft when on a trip or journey as it olfsetsthc ex pansion, etc., of the lifting gases when encoui teringvarious climatic changes and condltions. 'Rlgl'd alrcraft built and flown 1n accordance withcmy invention will be the great step forward in aeronautics:

Having thus described my invention, I claim 1. In a rigid aircraft, a framework consisting of upper and lower box beams and glrders fastened to and connecting sand box beams, part of said girders extending perpendicular to said box beams and others er:-

tending diagonally to said box beams.

2. In a r gid aircraft, a framework consisting of upper and lower boxbeams, backbone girders disposed between said boxbeams,

sisting of upper and lower boxbeams,backbone girders interposed to space said boxbeams, rib girders extending from the'boxbeams to provide an elliptical shaped body,

and .tensioning cables radiating from the center of the backbone girders to the rib girders to hold said girders and boxbeams assembled. V

5. An aircraft body comprising upper and lower boxbeams, backbone and rib girders attached to said boxbeams to provide an elliptical shaped body, and a plurality of gas chambers provided in the body, said and compressed-gas I storage tanks by rotary compressor and chambers being arranged in a plurality of pairs with a chamber of each pair disposed on opposite sides of theboxbeams.

6. In a rigid aircraft an aerostat comprising upper and lower boxbeams, vertically and diagonally backbone girders disposed be- .tween said boxbeams, and longitudinal and transverse partitions for providing a plural- I ity of pairs of chambers, one of each pair of chambers being disposed on opposite sides of the boxbeams.

7. An aerostat framework in cross section composed of upper and lower boxbeams, backbone "girders between said boxbeams, and rib girders provided with are portions terminating in relatively long straight ex tehsionsysaid rib girders being diametricalg ly attached to the boxbeams with the are portions forming the sides andthe extensions forming relatively long flat surfaces for the top and bottom of said framework.

8. In a rigid aircraft a frameworkcon-- sisting of upper. and lower boxbeams, backbone, girders disposed between said boxbeams,rib girders extending from the boxbeams to provide a body and a pluralityof gas chambers within the body, said chambers being arranged in a plurality of pairs with a chamber of each pair disposed on opposite sides of the boxbeams to provlde an aerostat, and arplu ality of planesoppositely disposed on the sides of the aerostat. v

9. Ina a rigid aircraft a framework consisting of upper and lower boxb'eams, backbone girders disposed between said boxbeams, rib girders extending from the boxbeams to provide a body and a plurality of gas chambers within the body, said chambers being arranged in a plurality of pairs with a chamber of each pair disposed on opposite sides of theboxbeams to providean aerostat, and a plurality of planes of unequal length disposed oppositely on the sides of the aerostat. I a

1(). In a rigid aircraft a framework con sisting of upper and lower'boxbeams, backbone girders disposed between said boxbeams, rib girders extending from the boxbeams to provide a body and a plurality of gas chambers within the body said chambers being arranged in a plurality of pairs with a. chamber of each pair disposed on opposite sides of the boxbeams tov provide an aerostat, and a plurality of planes progressively increasing in length from bottom to 'top being oppositely disposed on the sides of the aerostat.

ture.

FRANK BAUER.

.In testimony whereof, I affix my sigha- V 

